In this paper an investigation of an acoustic type waves influence on a wingtip vortex wake parameters was performed in a supersonic flow. The supersonic flow around a straight wing with sharp leading and trailing edges was considered at an attack angle of 10 degrees at Mach number of incoming flow M = 2.Perturbations were introduced into a steady state stream in the form of monochromatic plane waves with small amplitude. Numerical simulations were carried out at the Keldysh Institute of Applied Mathematics RAS using the parallel algorithm for turbulent flow simulation. For the numerical studies an approach based on the URANS method with using the SA turbulence model was applied. Numerical simulations were carried out on the supercomputing system K-60.Numerical data were obtained in the area exceeding 30 wing chords downstreamfrom a wing axis. A numerical data on the pulsation of gasdynamic parameters in the vortex wake influenced by disturbance are obtained, in particular, frequencies and disturbance ranges on the wingtip vortex axis are investigated depending on a distance from the wing - vortex generator.

Investigation of acoustic fluctuations in a flow with permeable boundaries using hot-wire anemometry

Influence of acoustic type waves on the vortex wake behind a wing in the supersonic flow

Turbulence in Supersonic Flow

Hot-wire measurements in the free stream of a supersonic wind tunnel were made in the Mach number range of 1.6 to 5.0. I t is shown that the mass-flow fluctuations increase very rapidly with increasing Mach number. If the fluctuation field is assumed to consist of sound waves—an assumption tha t is consistent with the measurements—the sound intensity is approximately proportional to M, within the range of the experiments. Furthermore, the orientation of the field is found to be different from the Mach line direction; it corresponds to a sound-source velocity of approximately one-half the free-stream velocity for the higher Mach numbers. I t is shown that the turbulent boundary layer along the nozzle and the tunnel walls is responsible for this sound field.

Investigation of acoustic fluctuations in a flow with permeable boundaries using hot-wire anemometry

Citations

Influence of acoustic type waves on the vortex wake behind a wing in the supersonic flow

References

Turbulence in Supersonic Flow

Aerodynamic noise in supersonic wind tunnels

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